Titanium-base alloys



United States Patent 3,378,368 TITANIUM-BASE ALLOYS Clive Dudley Thomas Minton, Shenstone, Lichiield, and

Michael George Edwards, Birmingham, England, assignors t0 Imperial Metal Industries (Kynoch) Limited, London, England, a corporation of Great Britain No Drawing. Filed June 7, 1965, Ser. No. 462,110 Claims priority, application Great Britain, Jan. 4, 1965, 278/65 19 Claims. (Cl. 75-1755) ABSTRACT OF THE DISCLOSURE Titanium-base alloys useful for the manufacture of high-temperature components which can be fabricated by welding. The alloys consist essentially of aluminum with or without tin as an alpha stabilizer, zirconium, silicon and niobium or tungsten as a beta stabilizer. Optionally copper may be present also.

This invention relates to titanium-base alloys and in.

particular to titanium-base alloys having good creep properties.

Titanium-base alloys have been used in applications requiring good creep resistance at temperatures up to about 450 C., such as in aircraft engines. An alloy which has particularly good creep strength and has been extensively used in aircraft engines, is one which has the normal composition Ti-l1Sn-2.25Al-5ZrlMo-O.2Si.

This alloy is not regarded as being weldable since Welds made in the alloy are to some extent brittle as a result of heating high in the beta field, and the loss of ductility cannot be restored by subsequent heat treatment. For this reason, the alloy cannot be used for applications which require the use of welding for fabrication and a limit is therefore placed on the usefulness of the alloy which otherwise has excellent properties.

We have discovered that this embrittlement is associated with the presence of molybdenum in the alloy and in order to improve the alloy as regards ductility after welding, it is necessary to replace the molybdenum by another element which does not cause embrittlement after welding or adversely affect the excellent creep resistance or unduly increase the density of the alloy.

Alloys in accordance with the invention consist of one or more of the alpha stabilisers, tin and aluminium, in an amount equal to an aluminium equivalent of 5.5-6.5% by weight, aluminium being present in an amount not less than 1.75 and tin, when present, not exceeding 11.5%, zirconium 37%; silicon 0.05-1.0%, up to 2% of one or more of the beta stabilisers niobium and tungsten, copper optionally being present in the range of 0.5-2.5%, balance titanium and usual impurities. Carbon may also be present in the range ODS-0.4%.

Also according to the invention a titanium-base alloy having high creep strength and good ductility after welding consists of one or more of the alpha stabilisers tin and aluminium in an amount equal to an aluminium-equivalent of 5.5-6.5%, aluminium being present in an amount not less than 1.75%, and tin, when present, not exceeding 11.5%, zirconium 3-7%, silicon ODS-0.25%, up to 2% of one or more of the beta stabilisers niobium and tungsten, copper optionally being present in the range 05-25%, balance titanium and usual impurities. Typical ranges of impurities are: carbon 0.01-0.05 oxygen 0.07-0.2% and nitrogen 0.002-0.02%.

In our prior Patents 3,105,759 and 3,049,425 we have shown that freedom from hydrogen embrittlement is inherent in the 11% tin, 2% aluminium base.

Tin may be wholly replaced by aluminium and as far as the effect of the tin on mechanical properties is concerned, one percent aluminium is equivalent to approximately three percent of tin. The aluminium-equivalent of the 11% tin, 2% aluminium content of the above-mentioned type of alloy is 6% aluminium and alloys at one end of the range of composition may have the 11% tin, 2% aluminium or, at the other end, the 6% aluminium alpha stabiliser content, but intermediate amounts of these alpha stabilisers are permissible. Another advantage of the tin-free composition is a lower density.

The preferred ranges of composition for the various alloying elements are as follows:

Percent Tin 10.5-11.5 and 0 Aluminium 1.75-2.75 and 5.5-6.5 Zirconium 4-6 Silicon 0.05-0.2 and 0.1-0.5 Niobium 0.5-2 Tungsten 0.5-2 Copper 0.5-2 Carbon 0.5-0.4

Substitution of niobium for molybdenum tends to lower the tensile strength by a small amount, but the ductility after a beta heat-treatment which simulates the thermal efiects of welding is increased markedly. If tungsten is substituted for molybdenum, the tensile strength is maintained and the ductility improved, but increasing the tungsten content up beyond 2% further increases the tensile strength but at the expense of ductility. Niobium and tungsten can be present together. Table I illustrates the etiect of varying quantities of niobium and tungsten additions and the effects of beta heat-treatment simulating thermal eiiects of welding. It is to be noted that when molybdenum is present, even with niobium and tungsten, there is some loss of ductility after heating into the beta phase field.

The addition of copper to the above-described alloys improves the tensile properties and in this respect copper behaves similarly to tungsten. Table II shows the eflect of copper additions.

Silicon in the range up to 0.25% gives adequate tensile strength for certain applications. A silicon content up to 1% provides higher tensile strength than silicon contents of up to 0.25 whilst the loss of ductility accompanying such increase in strength is comparatively small. Table V shows the effect on tensile strength of increasing the silicon content beyond 0.25

Carbon increases the tensile room temperature strength with a tolerable decrease in ductility and Without signifioanitly affecting the creep properties at 500 C. and 520 C. and a comparison of the first two alloys listed in Table V shows the effect of increased carbon content.

Creep tests on alloys containing 0.1% carbon and increased silicon are shown in Table VI and it will be seen by comparison with Table III that a. further small improvement results from the addition of silicon and carbon.

Alloys can be heat-treated in either the alpha+beta or beta fields before ageing and possess good creep resistance, optimum creep properties being obtained by heat-treatment in the beta field, followed by air-cooling or oil-quenching prior to ageing for 24 hours at 500 C. Table III shows the creep properties obtainable and it will also be seen that the alloys containing nominally 1% niobium or 0.75% tungsten compare favourably with the previously known :alloy containing molybdenum listed first in the table.

Alloys in accordance with the invention are thermally stable at elevated temperatures and Table IV shows the results of exposing such an alloy to the etfects of heating for prolonged periods. It will be seen that the niobiumbearing alloy does not lose ductility on exposure to service temperatures.

Table VII shows the effects of exposing an alloy containing 0.75% tungsten and 0.3% silicon to elevate temperatures. o

The alloys of the invention are particularly useful for the manufacture of compressor drums, wheels, blades and rings for aircraft engines, particularly for components which can be fabricated by welding. In order to meet the conditions of service, the alloys are required to possess 10 TABLE I.-TENSILE PROPERTIES J.

OF ALLOYS BASED UPON Ti-11 Sn-2$ Al-5 Zr-O.2 Si and i-(i Al-5 Zr0.2 Si

Composition 0.1% P.S., T.S., Percent Percent Heat-Treatment t.s.i. t.s.i. Elong. ILA.

s11 Al Zr si on 11 2% 5 0.2 1 Mo Alpha-beta 11.1. and aged.. 60. 2 70.1 14 34 11 2% 5 0.2 Beta .TJ 57. 3 72. 7 9 12 11 2% 5 0.2+1N b A1pha-beta 11.1. and aged... 57. 3 64. 2 18 35 11 2% 5 0.2-] Beta HT 49.8 63. 2 14 28 11 2% 5 0.2 Beta HIP. and aged 58. 1 70.0 t 10 34 11 2% 5 0.2 Beta H.l. 55. 70. 0 13 24 11 2% 0.3 Beta H.T. and aged 60. 3 73. 8 14 35 11 2% 5 0.3 ..do.-. Fractured in grips 11 2% 5 0.3 .do... 90. 5+ 99. 0 4 1 11 2 4 5 0.2 56. 4 71. 4 12 11 11 2% 5 02 Beta 1LT. 58. 7 73.2 10 17 11 2% 5 0.21 Nb-H hi0. Beta H.I. and aged... 05. 6 78.4 8 11 11 2% 5 0.2-1 Nb+1 1W0- Beta IL'I. 59.4 75.0 7 8 11 2 4 5 0.205 W+0.5 Mm... Beta 11.1. and aged- 63.2 74. 2 6 9 11 2% 5 0.2+0.5 \V+0.5 Mo.... Beta 1LT. 59.1 74. 0 10 12 6 5 0.2- Alpha-beta H.T. and aged. 58. 4 65. 4 17 36 G 5 0.2- Beta IL'I. and aged... 57.8 05.4 10 18 0 5 0.2- Beta 1LT. 52. 4 (i0. 5 14 27 0 5 0.2- Alpha-beta 1' 'I. and aged.. 52. 5 61. 5 17 33 6 5 0.2 Beta 1LT. 51. 4 61. 5 15 27 6 5 0.2- Alpha-beta H31. and aged. 53. 6 64. 9 15 6 5 0.2- Beta HIP 51.2 02.4 13 28 0 5 0.2 Alpha-beta 1LT. and aged. 50. 4 (i0. 8 16 (i 5 0.2--2 W Beta 1131. 51. 2 0i. 3 12 26 6 5 0.2--1 Nb+1 W Beta H11. and aged. 55.6 00. 2 10 21 6 5 0.21 Nb+1 \V Beta 1LT. 58.0 60. 0 13 l hr. 1,100 0., air-cool plus yield pt.

All aged samples heattreated 24 hours, 500 0., air-cool.

TABLE II.INFLUENCE OF COPPER ON THE PROPERTIES OF Ti-fiAl-5Zr-0.2 Si PLUS NIO' BIUB'I OR TUNGSTEN Composition 0.1% P.S T.S., Percent Percent Heat-Treatment t.s.1 t.s.i. Elong RA. Al Zr Si on /A G 5 0.2+0.5 W+0.5 Cu.... Beta heat-treated and aged 58. 2 04. 6 10 17 G 5 0.2+0.5 \V-l-O 5 Cu 54. 9 62. 4 14 21 0 5 0.2+1 W+1 Cu Beta heat-treated and aged. 59. 4 67. 3 12 19 U 5 0.2+1 \V-l-l Cu Beta hcattretaet 57.4 65. 2 12 18 0 5 0.2+0.5 Nb+0.5 Cu... Beta heat-treated and ag 56. 0 63. 4 12 18 (i 5 0.2+0.5 Nl)+0.5 Cu.-. Beta heat-treated 54. 6 61. 8 12 21 All alloys beta heat-treated hr. 1,100 0, air cooled and aged 24 hours 500 0.

TABLE III.OREEP TESTS ON ALLOYS CONTAINING NIOBIUM Composition Creep Test Data Initial Percent Total Plastic Plastic Strain Sn Al Zr S1 Heat-Treated Temp, Stress Strain, in-

C. t.s.i. Percent hr. 300 hr.

11 2% 5 0.2+l Mo... 1 hour 900 0., air cool {24 hours 500 0., air cool 450 23 NI] 057 088 11 2% 5 0.2+11\I0 lo 500 15 Nil 0.077 0.111 11 2% 5 0.2+1 Nl)... Alp] 450 25 Nil 0. 070 0.110 Nil 0 5 0.2+1 ND. 450 25 Nil Nil 0 5 0 3+1 Nb. 500 19 Nil Nil 6 5 0.2+1Nh... B ta H. 500 1?) Nil Nil 6 5 0.3+0.75 .V. Aplha-heta 1111. an aged... 450 25 Nil Nil 6 5 0.34-0.75 W. Beta I-I.I. and aged 450 25 Nil Nil 0 5 0.3 +0.75 W- Alpha-beta HT. and aged. 400 30 0. 007 Nil 6 5 0.34-0.75 V. Beta I-I.T.an;i aged 400 30 0.006 Nil 0 5 0.3+0.75 \V ..d0 520 20 Nil Nil 6 5 0.3+0.75 \V. Beta 1LT. and aged 1 520 20 Nil 1 Sample oil-quenched from solution treatment temperature. Samples air cooled from solution treatment temperature and aged 24 hours, 500 C.

Exposure Data Ti-ll Sn2% A1-5 Zr-l Mo-0.2 Si Ti-ll Sn% Al-5 Zr0.2 Sl-l Nb Temp., Time, Y.P., T.S., Percent R.A., 0.1% R8. T.S., Percent R.A.,

0. hrs. t.s.i. t.s.i. Elong. percent t.s.i. t.s.i. Elong. percent on NA on 1 Control.

All specimens heat-treated 1 hour, 900 0., air-cool plus 24 hours, 500 0.

TABLE V.TENSILE PROPERTIES OF ALLOYS BASED UPON 'II-fi AL-5 Composition 0.1% P.S T.S., Percent R.A.,

t.s.i t.s.i. Elong. Percent Sn Al 2: si n \/A 6 5 0.3+1 Nb+0.l C 58. 9 66. 4 12 14 6 5 0.5-H Nb 60. 5 69. 8 10 15 6 5 0.75-l-1 Nb 63. 8 71. 0 18 11 2% 5 0.3+1 Nb- 56. 4 66. 3 18 41 11 2% 5 0.5+1 Nb- 54. 7 67. 2 13 23 11 2% 5 0.75-l-1 Nb 59. 7 68. 5 18 36 11 2% 5 1 0+1 Nb--. 60. 5 72. 5 15 27 0. above alpha beta/beta transns TABLE VI.-CREEP TESTS ON THE CARBON-BEARING ALLOY Composition Creep Test Data Initial Percent Total Plastic Plastic Strain In- Heat-Treatment Temp., Stress, Strain, Al Zr Si Percent 100 hr. 300 hr.

C. t.s.i. 6 5 0.3+1 Nb-l-Ol 0.. Beta heat-treated". 500 20 Nil 0.035 0. 060 6 5 0.3+1 NIH-0.1 C .110 520 20 N11 0. 003

TABLE VII.-INFLUENCE OF EXPOSURE AT ELEVATED TEMPERATURES ON THE TEN- SILE PROPERTIES OF THE ALLOY TI-6 AL-5 zit-0.75 W'-0.3 SI

Exposure, Time of 0.1% P.S., U.T.S., Percent Condition Temp. 0. Exposure t.s.i. t.s.i. Elong.

4 hrs.) on \/A Beta heat-treated, air-cooled and aged 500 0 1 61.0 66. 4 10 500 100 62. 0 67. 4 11 500 300 61. 2 67. 7 11 Beta heat-treated, oil quenched and aged 525 0 61.2 68, 1 16 525 100 62. 7 70. 0 14 Properties determined on 0.6 in. dia. rod. Bcta-hcat-treated hour, l,045 O. and aged 24 hours, 500 C.

We claim:

1. A titanium-based alloy having high creep-strength and good ductility after welding consisting essentially of at least one alpha stabilizer selected from the group consisting of aluminum and tin, said aluminum always being present in an amount not less than 1.75% and tin, when present, not exceeding 11.5%, said total amount of aluminum and tin being in an amount equivalent to an aluminum equivalent of 55-65% by weight, said aluminum equivalent being calculated as one percent aluminum equivalent to approximately three percent tin, zirconium 3-7%, silicon 0.054% from about 0.5 to 2% of a beta stabilizer selected from the group consisting of niobium and tungsten, balance titanium and impurities.

2. A titanium-base alloy as claimed in claim 1 containing in addition 0.050.4% carbon.

3. A titanium-base alloy according to claim 1 containing 10.5-11.5% tin.

4. A titanium-base alloy according to claim 1 containing 1.75-2.75% aluminum.

5. A titanium-base alloy according to claim 1 containing 55-65% aluminum.

5. A titanium-base alloy according to claim 1 containing 46% zirconium.

7. A titanium-base alloy according to claim 1 containing 0.l-0.5% silicon.

8. A titanium-base alloy according to claim 1 containing 0.52% niobium.

9. A titanium-base alloy according to claim 1 containing 0.5-2% tungsten.

10. A titanium-base alloy according to claim 1 containing 0.5-2% copper.

11. A titanium-base alloy having high creep-strength and good ductility after welding consisting of 10.5ll.5% tin, 1.752.75% aluminum, 46% zirconium, 0.5-2% niobium, 0.5-1% silicon, balance titanium and impurities.

12. A titanium-base alloy having high creepstrength and good ductility after welding consisting of 10.5-1 1.5% tin, 1.752.75% aluminum, 46% zirconium, 0.5-2% tungsten, 0.54% silicon, balance titanium and impurities.

13. A titanium-base alloy having high creep-strength and good ductility after welding consisting of l0.51l.5% tin, 1.752.75% aluminum, 4-6% zirconium, 1% niobium, 1% tungsten, 0.5-1% silicon, balance titanium and impurities.

14. A titanium-base alloy having high creep-strength and good ductility after welding consisting of 5.56.5% aluminum, 4-6% zirconium, 0.5-2% niobium, 0.5-1% silicon, balance titanium and impurities.

15. A titanium-base alloy having high creep-strength and good ductility after welding consisting of 5.5-6%

aluminum, 46% zirconium, 0.5-2% tungsten, O.51% silicon, balance titanium and impurities.

16. A titanium-base alloy having high creep strength and good ductility after welding consisting of 5.56.5% aluminum, 46% zirconium, 1% niobium, 1% tungsten, 0.5-1% silicon, balance titanium and impurities.

17. A titanium-base alloy according to claim 13 containing in addition 0.050.4% carbon.

18. A titanium-base alloy having high creep-strength and good ductility after Welding consisting of 6% alumi- 1Q num, 5% zirconium, 0.75% tungsten, 0.51% silicon, balance titanium and impurities.

19. A titanium-base alloy having high creep-strength and good ductility after Welding consisting of 6% aluminum, 5% zirconium, 1% niobium, 0.3% silicon, 0.1% carbon, balance titanium and impurities.

References Cited UNITED STATES PATENTS 2,769,707 11/1956 Vordahl 75-l75.5 i 2,893,864 7/1959 Harris et al. 75l75.5 3,049,425 8/1962 Fentiman et al. 75-l75.5 3,105,759 10/1963 Fentirnan et a1. 75l75.5

FOREIGN PATENTS 944,954 12/1963 Great Britain.

CHARLES N. LOVELL, Primaly Examiner. 

